CN114560075B

CN114560075B - Dynamic mass center adjusting device for single body of combined aircraft

Info

Publication number: CN114560075B
Application number: CN202210061667.7A
Authority: CN
Inventors: 贾山; 蔡成志; 张青松; 陈金宝; 潘一华; 张金城
Original assignee: Nanjing University of Aeronautics and Astronautics
Current assignee: Nanjing University of Aeronautics and Astronautics
Priority date: 2022-01-19
Filing date: 2022-01-19
Publication date: 2023-05-09
Anticipated expiration: 2042-01-19
Also published as: CN114560075A

Abstract

The invention discloses a dynamic mass center adjusting device for a single body of a combined aircraft, which belongs to the technical field of aerospace and particularly comprises a gear, a rack, a motor and a roller. The motor is fixedly connected with the front baffle through the motor frame, the front baffle is fixedly connected with the rear baffle through the connecting rod, two rollers are symmetrically distributed on the front baffle and the rear baffle respectively, and the rollers can roll on the upper surface of the rack groove. The device drives the gear to roll on the rack through the motor, and drives the roller to roll on the upper surface of the rack groove to realize the adjustment of the mass center. The invention has the characteristics of small volume, high integration level, simple and reliable structure and the like, and can realize the adjustment of the single mass center of the combined aircraft.

Description

Dynamic mass center adjusting device for single body of combined aircraft

Technical Field

The invention relates to the technical field of aerospace, in particular to a dynamic mass center adjusting device for a single body of a combined aircraft.

Background

The unmanned combat platform for the combined body with the requirements of long voyage, large load and the like is divided into a main body at the position of a core node and two wings which can be decomposed into two isomorphic monomers. In order to enable the two-wing single body to have an independent pneumatic characteristic adjustment strategy during pre-separation, a single body mass center adjustment device is required to be arranged, specifically, components with larger mass such as a driving component, a control component and an energy component are arranged as movable parts inside the two-wing single body, so that the relative position between the wing section single body mass center and the pneumatic force pressing center is adjustable.

Under the fixed aerodynamic shape design, the change of the position of the single mass center of the aircraft not only affects static aerodynamic characteristics such as attack angle, resistance characteristic, lift-drag ratio and the like of the aircraft, but also affects dynamic aerodynamic characteristics such as rolling and yaw dynamic stability and the like, and the accurate configuration of the mass center of the aircraft is a key factor for determining the safe and accurate navigation of the aircraft.

For the aircraft adopting the variable centroid control technology, the research at home and abroad is mainly focused on the research of the metamorphic heart dynamics and metamorphic heart control methods, and the metamorphic heart control and other control modes (such as an air rudder, a reaction attitude control engine and the like) are mostly used at the same time at present. And the existing metamorphic ball screw actuating device is complex and redundant in structure, occupies a large volume, is more in transmission links, and greatly reduces the rigidity and transmission efficiency of the whole system. In addition, once an excessive load appears, radial load is caused on a ball screw pair in the system, the phenomenon of screw clamping and even damage can be caused to a great extent, and the reliability of the system is reduced.

Disclosure of Invention

The invention aims to solve the problems in the background technology and provides a dynamic mass center adjusting device for a single mass center of a combined aircraft, which realizes the change of the mass center of the single mass center of the whole aircraft by controlling the reciprocating motion of a mass block through a motor. The control of pitching and rolling postures of the aircraft is realized by adopting a pure metamorphic heart control mode without an air rudder and a reaction posture control engine, and the flying stability of the aircraft is ensured. It should be pointed out that the shape design of the combined aircraft and the single aircraft expressed by the following figures is only used as a reference, and the final state is not obtained, and the invention only describes the deterioration center device and does not relate to the pneumatic shape design of the single aircraft.

The invention is realized in the following way:

a dynamic mass center adjusting device for a combined aircraft monomer comprises a gear, a rack groove, a motor, a roller, a connecting rod, a front baffle, a rear baffle and a mass block. Specifically, the combined aircraft comprises a main body at the position of a core node and two isomorphic aircraft monomers which can be decomposed, and is characterized in that a mass center adjusting device is arranged in the aircraft monomers; the centroid adjusting device comprises a rack, a gear is arranged at the upper end of the rack, the gear is fixedly connected with the output end of the motor, and the gear can be driven by the motor to rotate and roll on the rack; the motor is fixedly connected with the front baffle through a motor frame, and the front baffle is fixedly connected with the rear baffle through two connecting rods;

the lower end of the rack is provided with a rack groove, the rack is arranged in the rack groove, sliding rails are arranged on two sides of the rack groove, and the front baffle plate and the rear baffle plate slide in the sliding rails on two sides of the rack groove.

Further, four identical mass center adjusting devices are arranged in the single aircraft, and rack grooves of the four mass center adjusting devices are distributed in a diamond shape.

Further, the inner sides of the front baffle and the rear baffle are respectively symmetrical with four rollers, and the four rollers can roll on the plane of the upper surface of the rack groove.

Further, two lighter mass blocks are arranged to be fixed on the outer side of the front baffle, and one heavier mass block is arranged to be fixed on the outer side of the rear baffle; and the total mass of the two lighter mass blocks, the motor and the motor frame outside the front baffle plate is equal to the mass of the heavier mass block outside the rear baffle plate.

Further, the aircraft monomer has a span length of 1m and a chord length of 0.5m, and the maximum takeoff weight is 35kg.

The beneficial effects of the invention compared with the prior art are as follows:

1. the centroid dynamic adjusting device provided by the invention has the advantages of small volume and light weight. The motor, the baffle, the roller and the gear adopt an integrated structural design. The movable mass block not only plays a part of the role of the movable mass block, but also has high integration level, and greatly reduces the volume of the whole system;

2. the gear and rack transmission design is adopted, so that the transmission links are few, the efficiency is high, and the rigidity is high. Compared with the traditional ball screw mechanism, parts with larger weight such as screw nuts, a workbench and the like are reduced, and the flexibility of the whole system is greatly improved;

3. the reliability of the load working condition is high. Compared with the traditional mass center adjusting mechanism, the device is mainly loaded by four rollers, so that the radial force load of the gear is weakened to the greatest extent, the service life of the gear and the rack is prolonged greatly, and the device is stronger in complex load adaptation capability and higher in reliability.

Drawings

FIG. 1 is a schematic diagram of the overall and individual structure of a composite aircraft.

FIG. 2 is a schematic diagram of a dynamic mass center adjusting device for an assembled aircraft according to the present invention;

FIG. 3a is a view from direction A-A of FIG. 2 of a modular aircraft center of mass dynamic adjustment apparatus in accordance with the present invention; FIG. 3B is a cross-sectional view taken along line B-B of FIG. 2 of a modular aircraft center of mass dynamic adjustment apparatus in accordance with the present invention;

FIG. 4a is a schematic diagram of a dynamic mass center adjusting device for an integrated aircraft according to the present invention; FIG. 4b is a schematic view of the distribution of the mass center adjusting device inside the aircraft;

FIG. 5a is a schematic diagram of a centroid adjusting device distribution when an aircraft adjusts pitch; FIG. 5b is a schematic diagram of a centroid adjusting device distribution when an aircraft is adjusting roll;

FIG. 6a is a two-dimensional schematic diagram of a dynamic adjustment device for the mass center of an integrated aircraft according to the present invention; FIG. 6b is a three-dimensional isometric view of the centroid range of a modular aircraft centroid dynamic adjustment device in accordance with the present invention;

the mass center adjusting device comprises a 1-mass center adjusting device, a 2-gear, a 3-rack, a 4-rack groove, a 501-motor, a 502-motor frame, a 6-roller, a 7-connecting rod, a 801-front baffle, a 802-rear baffle and a 9-mass block.

Detailed Description

The present invention will be described in further detail with reference to the following examples, for the purpose of making the objects, technical solutions, and effects of the present invention more apparent. It should be noted that the detailed description herein is for purposes of illustration only and is not intended to limit the invention.

As shown in fig. 1, the integral combined aircraft and the single body structure thereof are schematic diagrams, and the combined aircraft can be divided into a main body at the position of a core node and two wings which can be decomposed into two isomorphic single bodies, and the mass center dynamic adjusting device 1 is positioned in the single aircraft.

As shown in fig. 2, the dynamic adjusting device for the single mass center of the combined aircraft comprises a gear 2, a rack 3, a rack groove 4, a motor 501, a motor frame 502, a roller 6, a connecting rod 7, a front baffle 801, a rear baffle 802 and a mass block 9; the motor 501 is fixedly connected with the front baffle 801 through the motor frame 502, and the front baffle 801 is fixedly connected with the rear baffle 802 through two connecting rods 7. The gear 2 is fixedly connected with an output shaft of the motor 501 through a jackscrew, the widths of the gear 2 and the rack 3 are the same, and the gear 2 can be driven by the motor 501 to rotate and roll on the rack 3; the rack 3 is arranged in the rack groove 4, sliding rails are arranged at two sides of the rack groove 4, and the front baffle 801 and the rear baffle 802 can slide in the sliding rails at two sides of the rack groove.

As shown in fig. 2, two lighter masses 9 are secured to the outside of the front shield 801 and one heavier mass is secured to the outside of the rear shield 802; and the total mass of the front 801, the two lighter masses 9, the motor 501 and the motor frame 502 is equal to the mass of the heavier masses outside the rear 802.

As shown in fig. 2 to 3, four rollers 6 are symmetrically distributed on the inner sides of the front baffle 801 and the rear baffle 802 respectively, and are fixed on the baffles respectively through threaded connection, and the four rollers 6 can roll on the plane of the upper surface of the rack slot 4, as shown in fig. 3 b.

4 a-b are schematic distribution diagrams of a centroid dynamic adjustment device, wherein the x-axis direction is the aircraft spanwise direction and the y-axis direction is the aircraft chordwise direction; four identical mass center adjusting devices are arranged in a single aircraft body, and four racks are distributed in the aircraft body in a diamond shape.

As shown in fig. 5 a-b, a schematic diagram of movement of a center of mass adjustment device when an aircraft adjusts pitch and roll, respectively.

As shown in fig. 6 a-b, which are schematic diagrams of the centroid changing ranges of the centroid dynamic adjusting device, in this embodiment, assuming that the maximum length of the diamond rack in the chord direction (Y axis direction) is 0.3m and the maximum length of the spanwise direction (X axis direction) is 0.7m, the centroid changing ranges of the four centroid dynamic adjusting devices are shown in the shaded portion of fig. 5. The total mass of the combined aircraft monomer is 35kg, the span length and chord length are 0.5m and 1m respectively, and each mass of the four mass center adjusting devices is 3kg, so that the maximum change of the span direction (X-axis direction) of the mass center of the combined aircraft monomer is 12mm, and the maximum change of the chord direction (Y-axis direction) is 5.142mm.

The foregoing is merely a preferred embodiment of the invention, and it should be noted that modifications could be made by those skilled in the art without departing from the principles of the invention, which modifications would also be considered to be within the scope of the invention.

Claims

1. The utility model provides a dynamic adjusting device of composite aircraft monomer barycenter, the composite aircraft include the main part that resides in core node position and can decompose into two isomorphic aircraft monomer, its characterized in that, aircraft monomer inside be provided with barycenter adjusting device (1);

the mass center adjusting device (1) comprises a rack (3), a gear (2) is arranged at the upper end of the rack (3), the gear (2) is fixedly connected with the output end of the motor (501), and the gear (2) can be driven by the motor (501) to rotate and roll on the rack; the motor (501) is fixedly connected with the front baffle plate (801) through the motor frame (502), and the front baffle plate (801) is fixedly connected with the rear baffle plate (802) through two connecting rods (7);

the lower end of the rack (3) is provided with a rack groove (4), the rack (3) is arranged in the rack groove (4), sliding rails are arranged on two sides of the rack groove (4), and the front baffle plate (801) and the rear baffle plate (802) slide in the sliding rails on two sides of the rack groove (4); four identical mass center adjusting devices (1) are arranged in a single aircraft monomer, and rack grooves (4) of the four mass center adjusting devices (1) are distributed in a diamond shape; four rollers (6) are symmetrically arranged on the inner sides of the front baffle plate (801) and the rear baffle plate (802), and the four rollers (6) can roll on the plane of the upper surface of the rack groove (4).

2. A combined aircraft single centroid dynamic adjustment device according to claim 1, characterised in that two lighter masses (9) are arranged to be fixed to the outside of the front barrier (801) and one heavier mass is arranged to be fixed to the outside of the rear barrier (802); and the total mass of the two lighter masses, the motor (501) and the motor frame (502) outside the front baffle plate (801) is equal to the mass of the heavier mass outside the rear baffle plate (802).

3. The dynamic mass center adjusting device for an assembled aircraft monomer according to claim 1, wherein the aircraft monomer has a span length of 1m and a chord length of 0.5m, and the maximum takeoff weight is 35kg.